WO2015075345A1 - Modular engine, such as a jet engine, with a speed reduction gear - Google Patents

Modular engine, such as a jet engine, with a speed reduction gear Download PDF

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Publication number
WO2015075345A1
WO2015075345A1 PCT/FR2014/052846 FR2014052846W WO2015075345A1 WO 2015075345 A1 WO2015075345 A1 WO 2015075345A1 FR 2014052846 W FR2014052846 W FR 2014052846W WO 2015075345 A1 WO2015075345 A1 WO 2015075345A1
Authority
WO
WIPO (PCT)
Prior art keywords
module
shaft
turbine
nut
rotor
Prior art date
Application number
PCT/FR2014/052846
Other languages
French (fr)
Inventor
Michel Gilbert Roland Brault
Nathalie NOWAKOWSKI
Original Assignee
Snecma
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Snecma filed Critical Snecma
Priority to EP14806028.8A priority Critical patent/EP3071792B1/en
Priority to RU2016119153A priority patent/RU2674098C1/en
Priority to US15/037,397 priority patent/US10473035B2/en
Priority to CA2929947A priority patent/CA2929947C/en
Priority to BR112016011122-2A priority patent/BR112016011122B1/en
Priority to CN201480063462.6A priority patent/CN105765166B/en
Publication of WO2015075345A1 publication Critical patent/WO2015075345A1/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/025—Fixing blade carrying members on shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/026—Shaft to shaft connections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/51—Building or constructing in particular ways in a modular way, e.g. using several identical or complementary parts or features
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/60—Shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • Engine such as a turbojet engine, modular with speed reducer
  • the present invention relates to an aeronautical propulsion engine, such as a turbojet, a multi-flow turbofan, in particular with a high dilution ratio, or a turboprop, having a forward power transmission shaft, driven by a turbine rotor by the intermediate of a speed reducer.
  • a turbofan on this power transmission shaft is mounted including the fan.
  • Turbofan engines have several compressor stages, including a low pressure compressor (LP) also referred to as a booster compressor or booster and a high pressure compressor (HP) that belong to the primary body of the engine. Upstream of the low pressure compressor is disposed a large impeller wheel, or blower, which feeds both the primary flow that passes through the compressors BP and HP and the cold flow, or secondary flow, concentric to the first and is directed either directly to a cold flow nozzle, said secondary nozzle, or to a primary and secondary flow mixer.
  • LP low pressure compressor
  • HP high pressure compressor
  • the blower is driven by the rotation shaft of the BP body and generally rotates at the same speed as it. However, it may be advantageous to rotate the fan at a lower rotational speed than the LP shaft, especially when it is of very large size, in order to better adapt aerodynamically.
  • a gearbox between the LP shaft and a power transmission shaft, to which the blower is attached.
  • the fan, the shaft and the gearbox are, in general, part of the same module, upstream, called fan module.
  • Modern aeronautical engines are often made in the form of an assembly of modules which may include fixed parts and moving parts.
  • a module is defined as a subset of an engine that has geometric characteristics at its interfaces with adjacent modules that are sufficiently precise to be delivered individually and have been separately balanced when it contains parts. rotating.
  • the assembly of the modules makes it possible to constitute a complete engine, while minimizing the balancing and matching operations of the parts in interface.
  • the modularity of an engine is a key element for maintenance. Indeed, during an intervention, It is necessary that the parts are easily accessible without having to disassemble a large number of parts of the engine. In practice, we try to get a breakdown into a few major modules. For example, for a turbojet engine with a front fan, it is desired to divide into three modules: a first major module for the front part comprising the fan and the LP compressor, a second major module for the part comprising the HP body and a third major module for the rear part of the engine comprising the LP turbine and the turbine shaft.
  • the problem in this case is the accessibility to an inner turbine nut, by which two major modules are connected to each other.
  • the inner nut connects, at the front, the LP turbine shaft to the fan shaft.
  • the intervention on the first major module requires the disassembly of a portion of the gearbox to have access to the turbine nut because it is masked by the reducer. In this case, the modularity of the first major module is lost.
  • the second major module and the third major module must be disconnected independently.
  • a motor with a modular structure comprising a plurality of coaxial modules with at one end a first module comprising a power transmission shaft and a speed reducer, said transmission shaft.
  • power supply being driven through the speed reducer by a turbine shaft, secured to one of said coaxial modules separate from the first module, the speed reducer comprising as input drive means attached to the turbine shaft and to a journal of a shaft of a low-pressure compressor rotor, characterized by the fact that it comprises a first nut for fastening the drive means to the journal and a second nut for fastening the drive means to the turbine shaft.
  • the speed reducer is arranged to have a central opening configured to allow access of a mounting / disassembly tool, through said opening, to the second nut from said motor end.
  • the second nut is called turbine nut in the following.
  • a motor with a modular structure means a motor which is formed by the assembly of modules.
  • This type of engine is well known in the aeronautical field and facilitates in particular the assembly and disassembly of an engine, for example during a maintenance operation.
  • the invention proposes in particular to dissociate the fastening means of the drive means to the turbine shaft, fastening means of the drive means to the trunnion. Thanks to these characteristics, the problem of modularity of the motor is solved because the first module can be separated from the modules located behind without the speed reducer being disassembled beforehand.
  • the unscrewing of the second nut makes it possible to dissociate the driving means from the turbine shaft without dissociating the drive means from the journal which remain integral with each other thanks to the first nut. It is therefore possible to dismantle and remove the first module by unscrewing a single nut, this module not likely to dissociate further because of the unscrewing of the second nut.
  • the drive gear of the gearbox is annular in shape and has said central opening passage of a tool for mounting / disassembly of the turbine nut.
  • the drive means is itself connected to the input wheel of the speed reducer which is for example epicyclic gear with an input wheel secured to the sun gear and the power transmission shaft driven by the satellites.
  • the front end of the turbine shaft is supported by a bearing integral with the first module.
  • the driving means of the speed reducer form at least one wall for a sealed enclosure for lubricating and cooling said bearing.
  • the first nut has a diameter greater than that of the first nut.
  • the invention applies to a turbojet engine comprising a motor as described above, the first module comprises a fan mounted on said power shaft. More particularly, the invention applies to a turbojet engine with a second module, downstream of the first module, the second module comprising a rotor, formed of a high pressure compressor and a high pressure turbine, and a combustion chamber. . It applies in particular to a turbojet engine whose casing of the first module is secured to the casing of the second module by a removable fixing means.
  • the turbojet comprises a third module with a low pressure turbine, said turbine shaft being secured to the rotor of the low pressure turbine of the third module.
  • the invention also relates to a turbojet engine as described above comprising three successive modules, said first module with a fan rotor and the low pressure (LP) or booster compressor, a second module with a rotor formed of a high pressure compressor, a high pressure turbine and a combustion chamber and a third module with a low pressure turbine rotor and a coaxial turbine shaft with the high pressure rotor and, in use, connected to the fan rotor by the intermediate speed reducer, this turbojet engine is multiflux type.
  • the first module comprises a low pressure compressor rotor with a low pressure compressor shaft comprising a journal supported by a bearing integral with the first module and immobilized axially by a locking nut of the rotor of the low pressure compressor.
  • the first module or fan module comprises at least one support part of the fan shaft via two bearings, said support member having a first mounting flange of the module shaped to be attached to a second flange carried by a structural part of the turbojet, and the speed reducer is carried by a support casing comprising a shaped flange to be able to be fixed on said second structural flange of the turbojet, so as to be able to mount the gear reducer on said fan module prior to assembly of the fan module on at least one other module of the turbojet engine.
  • FIG. 1 is a general view in half axial section of a turbofan engine with a high dilution ratio incorporating a speed reducer
  • FIG. 2 is a partial view of the engine of FIG. 1 representing the front part with the gearbox
  • FIG. 3 is a view of the engine of FIG. 1, the first module of which is detached,
  • FIG. 4 is a view of the motor of FIG. 1, the three modules of which are separated from one another, - Figure 5 shows the detail of the turbine nut in place on the engine.
  • a turbojet engine 1 of axis XX which comprises, a fan S, a low pressure or booster compressor 1a, a high pressure compressor 1b, a combustion chamber 1c, a turbine high pressure 1 d, a low pressure turbine 1 e.
  • the high-pressure compressor 1b and the high-pressure turbine 1d are connected by a high-pressure shaft 4 and form with it an HP high-pressure body.
  • the low-pressure compressor 1 a and the low-pressure turbine 1 e are connected by a low-pressure shaft LP 2 and form with it a low-pressure body LP.
  • the disk on which the blades of the fan S are mounted is rotated by a power transmission shaft or fan shaft 3.
  • the latter is itself driven directly by the LP shaft 2.
  • the power transmission shaft 3 is driven by the LP shaft 2 through a speed reducer 7, this reducer is preferably epicyclic gear.
  • the engine is subdivided into three major modules; a first module A, called the fan module, comprises a fixed part comprising the fan casing forming the casing of the blower, the intermediate casing forming, inter alia, support of different bearings, 10, 1 1, 12, and an interface attached to the adjacent module B.
  • the moving part of the first module A comprises the fan S with its fan shaft 3 supported by the fan bearings 1 1 and 12, one of ball bearing abutment and the other bearing with rollers. It also includes the compressor BP 1 a supported by a low-pressure shaft bearing 10, ball-bearing.
  • bearing bearings are between a fixed ring and a movable ring.
  • the fixed ring 10 of the bearing of the low-pressure shaft is mounted on a bearing support 23 and the fixed rings of the bearings 1 1 and 12 of the fan are mounted on a bearing support 22, see FIG. speed 7 is housed between the blower and the LP shaft 2 in the space defined between the supports 22 and 23, integral with the intermediate casing.
  • the second major module B also includes moving parts such as the body HP with the compressor 1b and the turbine 1d and fixed parts such as the combustion chamber 1c and all the crankcase elements associated with it, of which the envelope 5.
  • the third module C comprises moving parts such as the LP turbine 1 e and the LP turbine shaft 2 and fixed parts such as the exhaust casing forming support of the bearings at the rear and the exhaust nozzle.
  • the modular structure is intended to allow a pre-assembly of the elements of the different modules independently of each other so that they are ready to be assembled without resorting to complex operations.
  • the first module A can be secured to the following modules by simply connecting the moving parts by means of a turbine nut, the turbine nut 14 connecting a drive gear of the speed reducer to the LP turbine shaft 2
  • the securing is also obtained by connecting the fixed parts by bolting the interface of the module A to a radial flange of the housing of the module B. An example of this latter mode of connection is shown in FIG.
  • Figure 3 shows the engine whose first module was separated from the rest of the engine. As indicated above, the first module is released by unscrewing the turbine nut 14 on the one hand and by unscrewing the bolts 24 which retain the fixed interface of the first module A to the radial flange 5R of the casing 5 of the second module, see Figure 6.
  • Figure 4 shows the separation of modules B and C from each other.
  • FIG. 2 shows in more detail the front part of the engine, in which the gearbox 7 is positioned between the power transmission shaft 3 attached to the fan and the LP shaft 2.
  • This reducing gear which is a prior epicyclic type, is represented in the schematic form of a rectangle showing only its bulk. It is carried, not shown, by the bearing supports 22 and 23 attached to the intermediate casing and is driven by an inlet ring 8 of the reducer extending upstream of the BP shaft 2, with which it cooperates by via driving means.
  • the output torque of this reducer 7 is transmitted to the fan shaft 3, by a conventional connection, known to those skilled in the art, such as for example an attachment of this fan shaft to the planet carrier, in the case of an epicyclic reduction gear.
  • a fixed part of the engine comprises the inner wall 21 of the primary flow stream, an upstream bearing support 22 and a downstream bearing support 23. These two supports extend towards the inside of the turbomachine while going wrap the bearings of the thrust bearing 10 supporting the LP shaft 2, and those of the thrust bearings 1 1 and rollers 12 of the fan shaft 3.
  • a moving part in addition to the rotor of the fan S, comprises , from upstream to downstream, the fan shaft 3 on which are attached the movable rings of the bearings 1 1 and 12 of the fan shaft, the ring gear 8 of the gearbox and an intermediate shaft 9 of extension of the the drive ring, which is fixed on the moving ring
  • This fixed and mobile parts form an enclosure E1 and are classically joined at the labyrinths positioned at its front and rear ends, so as to form a sealed volume which encloses the three bearings 10. , 1 1 and 12 mentioned above and ensures the permanence of their lubrication and cooling.
  • the aforementioned seals are not shown but are known to those skilled in the art.
  • This enclosure E1 is fully supported by the first module A, so that it can be detached from other modules and the LP shaft 2, without the oil that is enclosed does not escape.
  • the diameters of the input ring gear of the gearbox 8 and the intermediate shaft 9 of the LP shaft are defined to be greater than that of the BP 2 shaft, which means that it is possible to introducing a cylindrical tool to reach the fixing nut of the LP shaft 2 on the movable ring of its thrust bearing 10 and allow its unscrewing without these two parts interfering.
  • the LP shaft 2 meshes, by a system of grooves 132, on a pin 13 which is connected to the movable ring 10M of the thrust bearing 10 and which is extended downstream by the shaft of the low pressure compressor 1a and drives the rotor of the low pressure compressor 1a.
  • BP shaft 2 is held in place, axially, on this pin by means of a turbine nut 14 which is screwed on a thread 142 formed on the inner face of the BP shaft 2 and which bears against an axial abutment 15 extending radially inwards from the journal 13.
  • This nut 14, which attaches the LP shaft 2 to the journal 13, is accessible from the front of the engine, provided that the front cover is disassembled beforehand. its front tip, but without the need to disassemble others parts and in particular the constituent elements of the walls of the enclosure E1.
  • An object of the invention namely the possibility of disconnecting the first module A from the LP shaft 2 without disassembling the enclosure E1, is thus achieved.
  • the pin 13 carries, upstream, the intermediate shaft 9 which forms a means for driving the input ring gear 8 of the gearbox and which is located radially between the pin 13 and the movable ring 10M of the thrust bearing 10 of the BP shaft to which it is rigidly connected.
  • This intermediate shaft 9 is intended to extend the ring 8 and to allow the dismantling thereof with the pin 13, without this separation of the ring into two distinct elements, a ring proper 8 and an intermediate shaft 9 , which is essential for carrying out the invention.
  • the downstream end of this intermediate shaft 9 is positioned around the LP shaft 2 and makes it possible, because of the higher diameter of the shaft, access to the nut 14 for fixing the LP shaft from the front of the motor. It thus constitutes, with the input ring 8, a wall element of the front chamber E1 which is detachable from the BP shaft 2 but which can remain in place and maintain the volume integrity of the front chamber E1 when the BP shaft 2 is removed.
  • the drive crown 8 of the gearbox is mounted on the intermediate shaft 9 by means of splines which make the two shafts cooperate and which allow driving of the ring gear 8, and therefore of the gearbox 7, by the shaft BP 2 It has also, and for the same reasons as above, a diameter greater than that of the BP 2 tree.
  • a nut 16 is screwed onto an upstream end portion of the pin 13 and is in axial abutment against a shoulder 9e of the intermediate shaft 9.
  • the intermediate shaft 9 is itself axial support against the movable ring 10M of the bearing 10 supporting the upstream end of the turbine shaft BP2.
  • This nut 16 thus axially immobilizes the drive shaft of the low pressure compressor 1 a.
  • the rotor of Low pressure compressor also referred to as a booster compressor, is held in place in the first module A which can be handled without risk of damage for this moving part.
  • the nut 16 has a diameter greater than that of the nut 14 and therefore does not interfere with the passage of the assembly / disassembly tool of the nut 14.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)

Abstract

The present invention relates to an engine (1) with a modular structure comprising a plurality of coaxial modules (A, B, C) with, at one end, a first module (A) comprising a power transmission shaft (3) and a speed reduction gear (7), said power transmission shaft being driven via the speed reduction gear (7) by a turbine shaft (2) secured to one (C) of said coaxial modules that is separate from the first module, the speed reduction gear comprising a drive means (8 and 9) fixed to the turbine shaft (2) and to a journal (13) of a shaft of a low-pressure compressor rotor (1 a), characterized in that it comprises a first nut (16) for fastening the drive means to the journal and a second nut (14) for fastening the drive means to the turbine shaft.

Description

Moteur, tel qu'un turboréacteur, modulaire avec réducteur de vitesse  Engine, such as a turbojet engine, modular with speed reducer
Domaine de l'invention Field of the invention
La présente invention concerne un moteur de propulsion aéronautique, tel qu'un turboréacteur, une turbosoufflante multi-flux, notamment à fort taux de dilution, ou un turbopropulseur, présentant un arbre de transmission de puissance avant, entraîné par un rotor de turbine par l'intermédiaire d'un réducteur de vitesse. Dans le cas d'une turbosoufflante, sur cet arbre de transmission de puissance est montée notamment la soufflante. The present invention relates to an aeronautical propulsion engine, such as a turbojet, a multi-flow turbofan, in particular with a high dilution ratio, or a turboprop, having a forward power transmission shaft, driven by a turbine rotor by the intermediate of a speed reducer. In the case of a turbofan, on this power transmission shaft is mounted including the fan.
Etat de l'art State of the art
Les moteurs à turbosoufflante comportent plusieurs étages de compresseur, notamment un compresseur basse pression (BP) désigné aussi compresseur de gavage ou booster et un compresseur haute pression (HP) qui appartiennent au corps primaire du moteur. En amont du compresseur basse pression est disposée une roue d'aubes mobiles de grande dimension, ou soufflante, qui alimente à la fois le flux primaire qui traverse les compresseurs BP et HP et le flux froid, ou flux secondaire, concentrique au premier et qui est dirigé soit directement vers une tuyère de flux froid, dite tuyère secondaire, soit vers un mélangeur des flux primaire et secondaire. Turbofan engines have several compressor stages, including a low pressure compressor (LP) also referred to as a booster compressor or booster and a high pressure compressor (HP) that belong to the primary body of the engine. Upstream of the low pressure compressor is disposed a large impeller wheel, or blower, which feeds both the primary flow that passes through the compressors BP and HP and the cold flow, or secondary flow, concentric to the first and is directed either directly to a cold flow nozzle, said secondary nozzle, or to a primary and secondary flow mixer.
La soufflante est entraînée par l'arbre de rotation du corps BP et tourne généralement à la même vitesse que lui. Il peut cependant être intéressant de faire tourner la soufflante à une vitesse de rotation inférieure à celle de l'arbre BP, notamment lorsque celle-ci est de très grande dimension, dans le but de mieux l'adapter aérodynamiquement. Pour cela on dispose un réducteur entre l'arbre BP et un arbre de transmission de puissance, auquel la soufflante est attachée. La soufflante, l'arbre et le réducteur font, en général, partie d'un même module, amont, dénommé module de soufflante. The blower is driven by the rotation shaft of the BP body and generally rotates at the same speed as it. However, it may be advantageous to rotate the fan at a lower rotational speed than the LP shaft, especially when it is of very large size, in order to better adapt aerodynamically. For this we have a gearbox between the LP shaft and a power transmission shaft, to which the blower is attached. The fan, the shaft and the gearbox are, in general, part of the same module, upstream, called fan module.
Les moteurs aéronautiques modernes sont souvent réalisés sous la forme d'un assemblage de modules qui peuvent comporter des parties fixes et des parties mobiles. Un module est défini comme un sous-ensemble d'un moteur qui présente des caractéristiques géométriques au niveau de ses interfaces avec les modules adjacents suffisamment précises pour qu'il puisse être livré individuellement et qui a subi un équilibrage distinct lorsqu'il comporte des parties tournantes. L'assemblage des modules permet de constituer un moteur complet, en réduisant au maximum les opérations d'équilibrage et d'appariement des pièces en interface. Modern aeronautical engines are often made in the form of an assembly of modules which may include fixed parts and moving parts. A module is defined as a subset of an engine that has geometric characteristics at its interfaces with adjacent modules that are sufficiently precise to be delivered individually and have been separately balanced when it contains parts. rotating. The assembly of the modules makes it possible to constitute a complete engine, while minimizing the balancing and matching operations of the parts in interface.
La modularité d'un moteur est un élément clé pour la maintenance. En effet, lors d'une intervention, Il faut que les pièces soient accessibles facilement sans avoir à démonter un nombre important de parties du moteur. Dans la pratique, on essaye d'obtenir un découpage en quelques modules majeurs. Par exemple pour un turboréacteur à soufflante avant, on cherche un découpage en trois modules : un premier module majeur pour la partie avant comprenant la soufflante et le compresseur BP, un deuxième module majeur pour la partie comprenant le corps HP et un troisième module majeur pour la partie arrière du moteur comprenant la turbine BP et l'arbre de turbine. The modularity of an engine is a key element for maintenance. Indeed, during an intervention, It is necessary that the parts are easily accessible without having to disassemble a large number of parts of the engine. In practice, we try to get a breakdown into a few major modules. For example, for a turbojet engine with a front fan, it is desired to divide into three modules: a first major module for the front part comprising the fan and the LP compressor, a second major module for the part comprising the HP body and a third major module for the rear part of the engine comprising the LP turbine and the turbine shaft.
La maintenance est particulièrement difficile sur les moteurs comprenant un réducteur dans la partie avant. Le problème dans ce cas est l'accessibilité à un écrou interne de turbine, par lequel sont liés deux modules majeurs entre eux. On rappelle que dans un turboréacteur à double corps par exemple, l'écrou interne relie, à l'avant, l'arbre de turbine BP à l'arbre de soufflante. Sur les moteurs de l'art antérieur avec architecture à réducteur, l'intervention sur le premier module majeur nécessite le démontage d'une partie du réducteur pour avoir accès à l'écrou de turbine car celui-ci est masqué par le réducteur. Dans ce cas, la modularité du premier module majeur est perdue. De plus, il faut désolidariser le deuxième module majeur et le troisième module majeur de manière indépendante. Maintenance is particularly difficult on engines comprising a gearbox in the front part. The problem in this case is the accessibility to an inner turbine nut, by which two major modules are connected to each other. It will be recalled that in a double-body turbojet, for example, the inner nut connects, at the front, the LP turbine shaft to the fan shaft. On the engines of the prior art with geared architecture, the intervention on the first major module requires the disassembly of a portion of the gearbox to have access to the turbine nut because it is masked by the reducer. In this case, the modularity of the first major module is lost. In addition, the second major module and the third major module must be disconnected independently.
Exposé de l'invention Le présent déposant s'est fixé comme objectif la réalisation d'un moteur avec réducteur qui permet de résoudre ce problème de modularité. DESCRIPTION OF THE INVENTION The present applicant has set itself the goal of producing a geared motor which makes it possible to solve this problem of modularity.
On parvient à cet objectif, conformément à l'invention, avec un moteur à structure modulaire comportant une pluralité de modules coaxiaux avec, à une extrémité, un premier module comprenant un arbre de transmission de puissance et un réducteur de vitesse, ledit arbre de transmission de puissance étant entraîné par l'intermédiaire du réducteur de vitesse par un arbre de turbine, solidaire d'un desdits modules coaxiaux distinct du premier module, le réducteur de vitesse comprenant en entrée un moyen d'entraînement fixé à l'arbre de turbine et à un tourillon d'un arbre d'un rotor de compresseur basse pression, caractérisé par le fait qu'il comprend un premier écrou de fixation du moyen d'entraînement au tourillon et un second écrou de fixation du moyen d'entraînement à l'arbre de turbine. This object is achieved according to the invention with a motor with a modular structure comprising a plurality of coaxial modules with at one end a first module comprising a power transmission shaft and a speed reducer, said transmission shaft. power supply being driven through the speed reducer by a turbine shaft, secured to one of said coaxial modules separate from the first module, the speed reducer comprising as input drive means attached to the turbine shaft and to a journal of a shaft of a low-pressure compressor rotor, characterized by the fact that it comprises a first nut for fastening the drive means to the journal and a second nut for fastening the drive means to the turbine shaft.
De préférence, le réducteur de vitesse est agencé de manière à présenter une ouverture centrale configurée pour permettre l'accès d'un outil de montage/démontage, à travers ladite ouverture, au second écrou depuis ladite extrémité du moteur. Le second écrou est appelé écrou de turbine dans ce qui suit. Preferably, the speed reducer is arranged to have a central opening configured to allow access of a mounting / disassembly tool, through said opening, to the second nut from said motor end. The second nut is called turbine nut in the following.
Dans la présente demande, on entend par un moteur à structure modulaire, un moteur qui est formé par l'assemblage de modules. Ce type de moteur est bien connu dans le domaine aéronautique et facilite notamment les opérations de montage et démontage d'un moteur, par exemple lors d'une opération de maintenance. L'invention propose notamment de dissocier les moyens de fixation des moyens d'entraînement à l'arbre de turbine, des moyens de fixation des moyens d'entraînement au tourillon. Grâce à ces caractéristiques, on résout le problème de modularité du moteur car le premier module peut être séparé des modules situés en arrière sans que le réducteur de vitesse soit démonté au préalable. En effet, le dévissage du second écrou (ou écrou de turbine) permet de dissocier le moyen d'entraînement de l'arbre de turbine sans dissocier le moyen d'entraînement du tourillon qui restent solidaires l'un de l'autre grâce au premier écrou. Il est donc envisageable de démonter et de retirer le premier module en dévissant un seul écrou, ce module ne risquant pas de se dissocier davantage du fait du dévissage du second écrou. In the present application, a motor with a modular structure means a motor which is formed by the assembly of modules. This type of engine is well known in the aeronautical field and facilitates in particular the assembly and disassembly of an engine, for example during a maintenance operation. The invention proposes in particular to dissociate the fastening means of the drive means to the turbine shaft, fastening means of the drive means to the trunnion. Thanks to these characteristics, the problem of modularity of the motor is solved because the first module can be separated from the modules located behind without the speed reducer being disassembled beforehand. Indeed, the unscrewing of the second nut (or turbine nut) makes it possible to dissociate the driving means from the turbine shaft without dissociating the drive means from the journal which remain integral with each other thanks to the first nut. It is therefore possible to dismantle and remove the first module by unscrewing a single nut, this module not likely to dissociate further because of the unscrewing of the second nut.
De préférence, le moyen d'entraînement du réducteur de vitesse est de forme annulaire et présente ladite ouverture centrale de passage d'un outil de montage/démontage de l'écrou de turbine. Le moyen d'entraînement est lui-même relié à la roue d'entrée du réducteur de vitesse qui est par exemple à train épicycloïdal avec une roue d'entrée solidaire du planétaire et l'arbre de transmission de puissance entraîné par les satellites. Preferably, the drive gear of the gearbox is annular in shape and has said central opening passage of a tool for mounting / disassembly of the turbine nut. The drive means is itself connected to the input wheel of the speed reducer which is for example epicyclic gear with an input wheel secured to the sun gear and the power transmission shaft driven by the satellites.
Conformément à un mode de réalisation, l'extrémité avant de l'arbre de turbine est supportée par un palier solidaire du premier module. According to one embodiment, the front end of the turbine shaft is supported by a bearing integral with the first module.
Plus particulièrement, le moyen d'entraînement du réducteur de vitesse forme au moins une paroi pour une enceinte étanche de lubrification et de refroidissement dudit palier. Cette solution présente l'avantage de permettre le démontage du premier module tout en conservant l'huile de lubrification à l'intérieur de celui-ci. Il n'est pas nécessaire de vidanger l'huile de lubrification auparavant. More particularly, the driving means of the speed reducer form at least one wall for a sealed enclosure for lubricating and cooling said bearing. This solution has the advantage of allowing disassembly of the first module while retaining the lubricating oil inside thereof. It is not necessary to drain the lubricating oil beforehand.
Pour assurer le montage/démontage complet du premier module, celui-ci est retenu également par un moyen de fixation amovible à un élément de carter du moteur. Avantageusement, le premier écrou a un diamètre supérieur à celui du premier écrou. To ensure complete assembly / disassembly of the first module, it is also retained by a removable attachment means to a motor housing element. Advantageously, the first nut has a diameter greater than that of the first nut.
L'invention s'applique à un turboréacteur comportant un moteur tel que décrit ci-dessus, dont le premier module comprend une soufflante montée sur ledit arbre de puissance. Plus particulièrement, l'invention s'applique à un turboréacteur avec un deuxième module, en aval du premier module, le deuxième module comportant un rotor, formé d'un compresseur haute pression et d'une turbine haute pression, et une chambre de combustion. Elle s'applique notamment à un turboréacteur dont le carter du premier module est solidaire du carter du deuxième module par un moyen de fixation amovible. The invention applies to a turbojet engine comprising a motor as described above, the first module comprises a fan mounted on said power shaft. More particularly, the invention applies to a turbojet engine with a second module, downstream of the first module, the second module comprising a rotor, formed of a high pressure compressor and a high pressure turbine, and a combustion chamber. . It applies in particular to a turbojet engine whose casing of the first module is secured to the casing of the second module by a removable fixing means.
De préférence, le turboréacteur comprend un troisième module avec une turbine basse pression, ledit arbre de turbine étant solidaire du rotor de la turbine basse pression du troisième module. Enfin l'invention porte également sur un turboréacteur tel que décrit ci- dessus comprenant trois modules successifs, ledit premier module avec un rotor de soufflante et le compresseur basse pression (BP) ou de gavage, un deuxième module avec un rotor formé d'un compresseur haute pression, d'une turbine haute pression et une chambre de combustion et un troisième module avec un rotor de turbine basse pression et un arbre de turbine coaxial avec le rotor haute pression et, en service, relié au rotor de soufflante par l'intermédiaire du réducteur de vitesse, ce turboréacteur étant du type multiflux. Preferably, the turbojet comprises a third module with a low pressure turbine, said turbine shaft being secured to the rotor of the low pressure turbine of the third module. Finally, the invention also relates to a turbojet engine as described above comprising three successive modules, said first module with a fan rotor and the low pressure (LP) or booster compressor, a second module with a rotor formed of a high pressure compressor, a high pressure turbine and a combustion chamber and a third module with a low pressure turbine rotor and a coaxial turbine shaft with the high pressure rotor and, in use, connected to the fan rotor by the intermediate speed reducer, this turbojet engine is multiflux type.
De préférence, le premier module comprend un rotor de compresseur basse pression avec un arbre de compresseur basse pression comprenant un tourillon supporté par un palier solidaire du premier module et immobilisé axialement par un écrou de blocage du rotor du compresseur basse pression. Dans un mode particulier de réalisation, le premier module ou module de soufflante comprend au moins une pièce de support de l'arbre de soufflante par l'intermédiaire de deux roulements, ladite pièce de support comportant une première bride de fixation du module conformée pour être rattachée à une seconde bride portée par une pièce structurale du turboréacteur, et le réducteur de vitesse est porté par un carter de support comportant une bride conformée pour pouvoir se fixer sur ladite seconde bride structurale du turboréacteur, de façon à pouvoir monter le réducteur de vitesse sur ledit module de soufflante préalablement à l'assemblage du module de soufflante sur au moins un autre module du turboréacteur. Preferably, the first module comprises a low pressure compressor rotor with a low pressure compressor shaft comprising a journal supported by a bearing integral with the first module and immobilized axially by a locking nut of the rotor of the low pressure compressor. In a particular embodiment, the first module or fan module comprises at least one support part of the fan shaft via two bearings, said support member having a first mounting flange of the module shaped to be attached to a second flange carried by a structural part of the turbojet, and the speed reducer is carried by a support casing comprising a shaped flange to be able to be fixed on said second structural flange of the turbojet, so as to be able to mount the gear reducer on said fan module prior to assembly of the fan module on at least one other module of the turbojet engine.
Description des figures Description of figures
L'invention sera mieux comprise, et d'autres buts, détails, caractéristiques et avantages de celle-ci apparaîtront plus clairement au cours de la description explicative détaillée qui va suivre, d'un mode de réalisation de l'invention donné à titre d'exemple purement illustratif et non limitatif, en référence aux dessins schématiques annexés. The invention will be better understood, and other objects, details, features and advantages thereof will appear more clearly in the following detailed explanatory description of an embodiment of the invention given as a purely illustrative and non-limiting example, with reference to the accompanying schematic drawings.
Sur ces dessins : On these drawings:
- la figure 1 est une vue générale en demi coupe axiale d'un turboréacteur double flux à fort taux de dilution incorporant un réducteur de vitesse, FIG. 1 is a general view in half axial section of a turbofan engine with a high dilution ratio incorporating a speed reducer,
- la figure 2 est une vue partielle du moteur de la figure 1 représentant la partie avant avec le réducteur, FIG. 2 is a partial view of the engine of FIG. 1 representing the front part with the gearbox,
- la figure 3 est une vue du moteur de la figure 1 dont le premier module est détaché, FIG. 3 is a view of the engine of FIG. 1, the first module of which is detached,
- la figure 4 est une vue du moteur de la figure 1 dont les trois modules sont séparés les uns des autres, - la figure 5 montre le détail de l'écrou de turbine en place sur le moteur. FIG. 4 is a view of the motor of FIG. 1, the three modules of which are separated from one another, - Figure 5 shows the detail of the turbine nut in place on the engine.
- la figure 6 montre le détail de la fixation de l'interface du premier module sur une bride du deuxième module. Présentation détaillée d'un mode de réalisation - Figure 6 shows the detail of the attachment of the interface of the first module on a flange of the second module. Detailed presentation of an embodiment
En se référant à la figure 1 , on voit un turboréacteur 1 d'axe XX qui comporte, une soufflante S, un compresseur basse pression ou de gavage 1 a, un compresseur haute pression 1 b, une chambre de combustion 1 c, une turbine haute pression 1 d, une turbine basse pression 1 e. Le compresseur haute pression 1 b et la turbine haute pression 1 d sont reliés par un arbre haute pression 4 et forment avec lui un corps haute pression HP. Le compresseur basse pression 1 a et la turbine basse pression 1 e sont reliés par un arbre basse pression BP 2 et forment avec lui un corps basse pression BP. Dans les configurations classiques, le disque sur lequel sont montées les aubes de la soufflante S est entraîné en rotation par un arbre de transmission de puissance ou arbre de soufflante 3. Celui-ci est lui-même entraîné directement par l'arbre BP 2. Dans le moteur de l'invention, l'arbre de transmission de puissance 3 est entraîné par l'arbre BP 2 au travers d'un réducteur de vitesse 7, ce réducteur étant de préférence à train épicycloïdal. Referring to FIG. 1, a turbojet engine 1 of axis XX is shown which comprises, a fan S, a low pressure or booster compressor 1a, a high pressure compressor 1b, a combustion chamber 1c, a turbine high pressure 1 d, a low pressure turbine 1 e. The high-pressure compressor 1b and the high-pressure turbine 1d are connected by a high-pressure shaft 4 and form with it an HP high-pressure body. The low-pressure compressor 1 a and the low-pressure turbine 1 e are connected by a low-pressure shaft LP 2 and form with it a low-pressure body LP. In conventional configurations, the disk on which the blades of the fan S are mounted is rotated by a power transmission shaft or fan shaft 3. The latter is itself driven directly by the LP shaft 2. In the engine of the invention, the power transmission shaft 3 is driven by the LP shaft 2 through a speed reducer 7, this reducer is preferably epicyclic gear.
Le moteur est ici subdivisé en trois modules majeurs; un premier module A, dit module de soufflante, comprend une partie fixe comprenant le carter de soufflante formant l'enveloppe de la soufflante, le carter intermédiaire formant, entre autres, support de différents paliers, 10, 1 1 , 12, et un interface de fixation au module adjacent B. La partie mobile du premier module A comprend la soufflante S avec son arbre de soufflante 3 supporté par les paliers de soufflante 1 1 et 12, l'un de butée à roulement à billes et l'autre à roulement à rouleaux. Elle comprend aussi le compresseur BP 1 a supporté par un palier d'arbre basse pression 10, à roulement à billes. Comme cela est connu les roulements des paliers sont compris entre une bague fixe et une bague mobile. La bague fixe 10 du palier de l'arbre basse pression est montée sur un support de palier 23 et les bagues fixes des paliers 1 1 et 12 de la soufflante sont montées sur un support de palier 22, voir la figure 2. Le réducteur de vitesse 7 est logé entre la soufflante et l'arbre BP 2 dans l'espace défini entre les supports 22 et 23, solidaires du carter intermédiaire. The engine is subdivided into three major modules; a first module A, called the fan module, comprises a fixed part comprising the fan casing forming the casing of the blower, the intermediate casing forming, inter alia, support of different bearings, 10, 1 1, 12, and an interface attached to the adjacent module B. The moving part of the first module A comprises the fan S with its fan shaft 3 supported by the fan bearings 1 1 and 12, one of ball bearing abutment and the other bearing with rollers. It also includes the compressor BP 1 a supported by a low-pressure shaft bearing 10, ball-bearing. As is known bearing bearings are between a fixed ring and a movable ring. The fixed ring 10 of the bearing of the low-pressure shaft is mounted on a bearing support 23 and the fixed rings of the bearings 1 1 and 12 of the fan are mounted on a bearing support 22, see FIG. speed 7 is housed between the blower and the LP shaft 2 in the space defined between the supports 22 and 23, integral with the intermediate casing.
Le deuxième module majeur B comprend également des parties mobiles telles que le corps HP avec le compresseur 1 b et la turbine 1 d et des parties fixes telles que la chambre de combustion 1 c et tous les éléments de carter qui lui sont associés, dont l'enveloppe 5. The second major module B also includes moving parts such as the body HP with the compressor 1b and the turbine 1d and fixed parts such as the combustion chamber 1c and all the crankcase elements associated with it, of which the envelope 5.
Le troisième module C comprend des parties mobiles comme la turbine BP 1 e et l'arbre de turbine BP 2 et des parties fixes comme le carter d'échappement formant support des paliers à l'arrière et la tuyère d'échappement. The third module C comprises moving parts such as the LP turbine 1 e and the LP turbine shaft 2 and fixed parts such as the exhaust casing forming support of the bearings at the rear and the exhaust nozzle.
La structure modulaire a pour but de permettre un pré-assemblage des éléments des différents modules indépendamment les uns des autres de manière à ce qu'ils soient prêts à être assemblés sans recourir à des opérations complexes. Ainsi le premier module A peut être solidarisé aux modules suivants par simple liaison des parties mobiles au moyen d'un écrou de turbine, l'écrou de turbine 14 reliant un moyen d'entraînement du réducteur de vitesse à l'arbre de turbine BP 2. La solidarisation est aussi obtenue par liaison des parties fixes par boulonnage de l'interface du module A à une bride radiale du carter du module B. Un exemple de ce dernier mode de liaison est montré sur la figure 6. The modular structure is intended to allow a pre-assembly of the elements of the different modules independently of each other so that they are ready to be assembled without resorting to complex operations. Thus the first module A can be secured to the following modules by simply connecting the moving parts by means of a turbine nut, the turbine nut 14 connecting a drive gear of the speed reducer to the LP turbine shaft 2 The securing is also obtained by connecting the fixed parts by bolting the interface of the module A to a radial flange of the housing of the module B. An example of this latter mode of connection is shown in FIG.
La figure 3 montre le moteur dont le premier module a été séparé du reste du moteur. Comme indiqué plus haut, on libère le premier module en dévissant l'écrou de turbine 14 d'une part et en dévissant les boulons 24 qui retiennent l'interface fixe du premier module A à la bride radiale 5R du carter 5 du deuxième module, voir figure 6. Figure 3 shows the engine whose first module was separated from the rest of the engine. As indicated above, the first module is released by unscrewing the turbine nut 14 on the one hand and by unscrewing the bolts 24 which retain the fixed interface of the first module A to the radial flange 5R of the casing 5 of the second module, see Figure 6.
La figure 4 montre la séparation des modules B et C l'un de l'autre. En libérant les éléments de carter respectifs les uns des autres, on permet la séparation des deux modules axialement l'un de l'autre ; l'arbre de turbine 2 n'est plus retenu par l'écrou de turbine et peut être dégagé du deuxième module. Figure 4 shows the separation of modules B and C from each other. By releasing the respective housing elements from each other, it is possible to separate the two modules axially from each other; the turbine shaft 2 is no longer retained by the turbine nut and can be released from the second module.
La figure 2 montre plus en détail la partie avant du moteur, dans lequel le réducteur 7 est positionné entre l'arbre 3 de transmission de puissance attaché à la soufflante et l'arbre BP 2. Ce réducteur, a priori de type épicycloïdal, est représenté sous la forme schématique d'un rectangle ne montrant que son encombrement. Il est porté, de façon non représentée, par les supports de paliers 22 et 23 rattachés au carter intermédiaire et est entraîné par une couronne d'entrée 8 du réducteur s'étendant en amont de l'arbre BP 2, avec lequel elle coopère par l'intermédiaire de moyens d'entraînement. Le couple en sortie de ce réducteur 7 est transmis à l'arbre de soufflante 3, par une liaison classique, connue de l'homme du métier, comme par exemple une fixation de cet arbre de soufflante au porte- satellites, dans le cas d'un réducteur épicycloïdal. Sur la figure, une partie fixe du moteur comprend la paroi interne 21 de la veine du flux primaire, un support amont de palier 22 et un support aval de palier 23. Ces deux supports s'étendent vers l'intérieur de la turbomachine en allant envelopper les paliers du roulement de butée 10 supportant l'arbre BP 2, et ceux des roulements de butée à billes 1 1 et de rouleaux 12 de l'arbre de soufflante 3. Une partie mobile, outre le rotor de la soufflante S, comprend, d'amont en aval, l'arbre de soufflante 3 sur lequel sont attachées les bagues mobiles des roulements 1 1 et 12 de l'arbre de soufflante, la couronne 8 d'entraînement du réducteur et un arbre intermédiaire 9 d'extension de la couronne d'entraînement, qui est fixée sur la bague mobile du roulement de butée 10 de l'arbre BP 2. Ces parties fixes et mobiles forment une enceinte E1 et sont classiquement jointes au niveau de labyrinthes positionnés à ses extrémités avant et arrière, de façon à former un volume étanche qui renferme les trois roulements 10, 1 1 et 12 mentionnés ci-dessus et qui assure la permanence de leur lubrification et de leur refroidissement. Les joints d'étanchéité précités ne sont pas représentés mais sont connus en tant que tels de l'homme du métier. FIG. 2 shows in more detail the front part of the engine, in which the gearbox 7 is positioned between the power transmission shaft 3 attached to the fan and the LP shaft 2. This reducing gear, which is a prior epicyclic type, is represented in the schematic form of a rectangle showing only its bulk. It is carried, not shown, by the bearing supports 22 and 23 attached to the intermediate casing and is driven by an inlet ring 8 of the reducer extending upstream of the BP shaft 2, with which it cooperates by via driving means. The output torque of this reducer 7 is transmitted to the fan shaft 3, by a conventional connection, known to those skilled in the art, such as for example an attachment of this fan shaft to the planet carrier, in the case of an epicyclic reduction gear. In the figure, a fixed part of the engine comprises the inner wall 21 of the primary flow stream, an upstream bearing support 22 and a downstream bearing support 23. These two supports extend towards the inside of the turbomachine while going wrap the bearings of the thrust bearing 10 supporting the LP shaft 2, and those of the thrust bearings 1 1 and rollers 12 of the fan shaft 3. A moving part, in addition to the rotor of the fan S, comprises , from upstream to downstream, the fan shaft 3 on which are attached the movable rings of the bearings 1 1 and 12 of the fan shaft, the ring gear 8 of the gearbox and an intermediate shaft 9 of extension of the the drive ring, which is fixed on the moving ring This fixed and mobile parts form an enclosure E1 and are classically joined at the labyrinths positioned at its front and rear ends, so as to form a sealed volume which encloses the three bearings 10. , 1 1 and 12 mentioned above and ensures the permanence of their lubrication and cooling. The aforementioned seals are not shown but are known to those skilled in the art.
Cette enceinte E1 est entièrement portée par le premier module A, ce qui fait qu'elle peut être désolidarisée des autres modules ainsi que de l'arbre BP 2, sans que l'huile qui y est enfermée ne s'échappe. Par ailleurs les diamètres de la couronne d'entrée du réducteur 8 et de l'arbre intermédiaire 9 de l'arbre BP sont définis pour être supérieurs à celui de l'arbre BP 2, ce qui signifie qu'il est possible d'y introduire un outillage cylindrique pour atteindre l'écrou de fixation de l'arbre BP 2 sur la bague mobile de son roulement de butée 10 et permettre son dévissage sans que ces deux pièces n'interfèrent. This enclosure E1 is fully supported by the first module A, so that it can be detached from other modules and the LP shaft 2, without the oil that is enclosed does not escape. Moreover, the diameters of the input ring gear of the gearbox 8 and the intermediate shaft 9 of the LP shaft are defined to be greater than that of the BP 2 shaft, which means that it is possible to introducing a cylindrical tool to reach the fixing nut of the LP shaft 2 on the movable ring of its thrust bearing 10 and allow its unscrewing without these two parts interfering.
Sur la figure 5, on a représenté plus en détail l'écrou de turbine lorsqu'il est en place sur l'arbre de turbine. In Figure 5, there is shown in more detail the turbine nut when in place on the turbine shaft.
En partant de l'aval, l'arbre BP 2 engrène, par un système de cannelures 132, sur un tourillon 13 qui est relié à la bague mobile 10M du roulement de butée 10 et qui est prolongé vers l'aval par l'arbre du compresseur basse pression 1 a et entraîne le rotor du compresseur basse pression 1 a. L'arbre BP 2 est maintenu en place, axialement, sur ce tourillon par l'intermédiaire d'un écrou de turbine 14 qui se visse sur un filetage 142 pratiqué sur la face interne de l'arbre BP 2 et qui vient prendre appui contre une butée axiale 15 s'étendant radialement vers l'intérieur à partir du tourillon 13. Cet écrou 14, qui attache l'arbre BP 2 au tourillon 13, est accessible depuis l'avant du moteur, moyennant toutefois le démontage préalable du capot de sa pointe avant, mais sans qu'il soit besoin de démonter d'autres pièces et notamment des éléments constitutifs des parois de l'enceinte E1 . Un but de l'invention, à savoir la possibilité désolidariser le premier module A de l'arbre BP 2 sans désassembler l'enceinte E1 , est ainsi atteint. From downstream, the LP shaft 2 meshes, by a system of grooves 132, on a pin 13 which is connected to the movable ring 10M of the thrust bearing 10 and which is extended downstream by the shaft of the low pressure compressor 1a and drives the rotor of the low pressure compressor 1a. BP shaft 2 is held in place, axially, on this pin by means of a turbine nut 14 which is screwed on a thread 142 formed on the inner face of the BP shaft 2 and which bears against an axial abutment 15 extending radially inwards from the journal 13. This nut 14, which attaches the LP shaft 2 to the journal 13, is accessible from the front of the engine, provided that the front cover is disassembled beforehand. its front tip, but without the need to disassemble others parts and in particular the constituent elements of the walls of the enclosure E1. An object of the invention, namely the possibility of disconnecting the first module A from the LP shaft 2 without disassembling the enclosure E1, is thus achieved.
Comme on le voit également sur la figure 5, le tourillon 13 porte, vers l'amont, l'arbre intermédiaire 9 qui forme un moyen d'entraînement de la couronne d'entrée 8 du réducteur et qui est situé radialement entre le tourillon 13 et la bague mobile 10M du roulement de butée 10 de l'arbre BP à laquelle il est rigidement lié. Cet arbre intermédiaire 9 a pour objet de prolonger la couronne 8 et de permettre le démontage de celle-ci d'avec le tourillon 13, sans que cette séparation de la couronne en deux éléments distincts, une couronne proprement dite 8 et un arbre intermédiaire 9, soit essentielle à la réalisation de l'invention. L'extrémité aval de cet arbre intermédiaire 9 est positionnée autour de l'arbre BP 2 et permet, du fait du diamètre plus élevé de l'arbre, un accès à l'écrou 14 de fixation de l'arbre BP depuis l'avant du moteur. Il constitue de ce fait, avec la couronne d'entrée 8, un élément de paroi de l'enceinte avant E1 qui est détachable de l'arbre BP 2 mais qui peut rester en place et maintenir l'intégrité volumique de l'enceinte avant E1 lorsque l'arbre BP 2 est retiré. As can also be seen in FIG. 5, the pin 13 carries, upstream, the intermediate shaft 9 which forms a means for driving the input ring gear 8 of the gearbox and which is located radially between the pin 13 and the movable ring 10M of the thrust bearing 10 of the BP shaft to which it is rigidly connected. This intermediate shaft 9 is intended to extend the ring 8 and to allow the dismantling thereof with the pin 13, without this separation of the ring into two distinct elements, a ring proper 8 and an intermediate shaft 9 , which is essential for carrying out the invention. The downstream end of this intermediate shaft 9 is positioned around the LP shaft 2 and makes it possible, because of the higher diameter of the shaft, access to the nut 14 for fixing the LP shaft from the front of the motor. It thus constitutes, with the input ring 8, a wall element of the front chamber E1 which is detachable from the BP shaft 2 but which can remain in place and maintain the volume integrity of the front chamber E1 when the BP shaft 2 is removed.
Enfin la couronne 8 d'entraînement du réducteur est montée sur l'arbre intermédiaire 9 au moyen de cannelures qui font coopérer les deux arbres et qui permettent l'entraînement de la couronne 8, et donc du réducteur 7, par l'arbre BP 2. Elle a également, et pour les mêmes raisons que précédemment, un diamètre supérieur à celui de l'arbre BP 2. Finally, the drive crown 8 of the gearbox is mounted on the intermediate shaft 9 by means of splines which make the two shafts cooperate and which allow driving of the ring gear 8, and therefore of the gearbox 7, by the shaft BP 2 It has also, and for the same reasons as above, a diameter greater than that of the BP 2 tree.
Comme on le voit sur la figure 5, un écrou 16 est vissé sur une portion d'extrémité amont du tourillon 13 et est en butée axiale contre un épaulement 9e de l'arbre intermédiaire 9. L'arbre intermédiaire 9 est lui-même en appui axial contre la bague mobile 10M du palier 10 supportant l'extrémité amont de l'arbre de turbine BP2. Cet écrou 16 immobilise ainsi axialement l'arbre d'entraînement du compresseur basse pression 1 a. Par cet écrou, le rotor du compresseur basse pression, désigné aussi compresseur de gavage, est maintenu en place dans le premier module A qui peut être manipulé sans risque d'endommagement pour cette partie mobile. As can be seen in FIG. 5, a nut 16 is screwed onto an upstream end portion of the pin 13 and is in axial abutment against a shoulder 9e of the intermediate shaft 9. The intermediate shaft 9 is itself axial support against the movable ring 10M of the bearing 10 supporting the upstream end of the turbine shaft BP2. This nut 16 thus axially immobilizes the drive shaft of the low pressure compressor 1 a. By this nut, the rotor of Low pressure compressor, also referred to as a booster compressor, is held in place in the first module A which can be handled without risk of damage for this moving part.
L'écrou 16 a un diamètre supérieur à celui de l'écrou 14 et ne gêne donc pas le passage de l'outil de montage/démontage de l'écrou 14. The nut 16 has a diameter greater than that of the nut 14 and therefore does not interfere with the passage of the assembly / disassembly tool of the nut 14.

Claims

R E V E N D I C A T I O N S
1 . Moteur (1 ) à structure modulaire comportant une pluralité de modules coaxiaux (A, B, C) avec, à une extrémité dudit moteur, un premier module (A) comprenant un arbre de transmission de puissance (3) et un réducteur de vitesse (7), ledit arbre de transmission de puissance étant entraîné par l'intermédiaire du réducteur de vitesse (7) par un arbre de turbine (2) solidaire d'un (C) desdits modules coaxiaux distinct du premier module dudit moteur, le réducteur de vitesse (7) comprenant un moyen d'entraînement (8 et 9) fixé à l'arbre de turbine (2) et à un tourillon (13) d'un arbre d'un rotor de compresseur basse pression (1 a), caractérisé par le fait qu'il comprend un premier écrou (16) de fixation du moyen d'entraînement au tourillon et un second écrou (14) de fixation du moyen d'entraînement à l'arbre de turbine. 1. Motor (1) with a modular structure comprising a plurality of coaxial modules (A, B, C) with, at one end of said motor, a first module (A) comprising a power transmission shaft (3) and a speed reducer ( 7), said power transmission shaft being driven via the speed reducer (7) by a turbine shaft (2) integral with one (C) of said coaxial modules distinct from the first module of said motor, the gear reducer gear (7) comprising drive means (8 and 9) fixed to the turbine shaft (2) and to a journal (13) of a shaft of a low pressure compressor rotor (1 a), characterized by the fact that it comprises a first nut (16) for fixing the drive means to the journal and a second nut (14) for fixing the drive means to the turbine shaft.
2. Moteur selon la revendication 1 dont le réducteur de vitesse (7) est agencé de manière à présenter une ouverture centrale configurée pour permettre l'accès par un outil de montage/démontage, à travers ladite ouverture, au second écrou (14) depuis ladite extrémité du moteur 2. Motor according to claim 1, the speed reducer (7) of which is arranged so as to have a central opening configured to allow access by an assembly/disassembly tool, through said opening, to the second nut (14) from said end of the engine
3. Moteur selon la revendication 1 ou 2 dont le moyen d'entraînement (9) du réducteur de vitesse est de forme annulaire et présente ladite ouverture centrale de passage d'un outil de montage/démontage de l'écrou de turbine. 3. Motor according to claim 1 or 2, the drive means (9) of the speed reducer is of annular shape and has said central opening for the passage of a tool for mounting/dismounting the turbine nut.
4. Moteur selon l'une des revendications 1 à 3 dont l'extrémité avant de l'arbre de turbine (2) est supportée par un palier (10) solidaire du premier module (A). 4. Engine according to one of claims 1 to 3, the front end of the turbine shaft (2) is supported by a bearing (10) secured to the first module (A).
5. Moteur selon les revendications 3 et 4 prises ensemble dont le moyen d'entraînement (9) du réducteur de vitesse forme au moins une des parois mobiles pour une enceinte étanche (E1 ) de lubrification et de refroidissement dudit palier (10). 5. Motor according to claims 3 and 4 taken together, the drive means (9) of the speed reducer forming at least one of the movable walls for a sealed enclosure (E1) for lubrication and cooling of said bearing (10).
6. Moteur selon l'une des revendications 1 à 5 dont le premier module (A) est retenu par un moyen de fixation amovible (24) à un élément de carter du moteur. 6. Motor according to one of claims 1 to 5, the first module (A) of which is retained by removable fixing means (24) to an element of the motor casing.
7. Moteur selon l'une des revendications 1 à 6 dont le premier écrou (16) a un diamètre supérieur à celui du premier écrou (14)7. Motor according to one of claims 1 to 6, the first nut (16) of which has a diameter greater than that of the first nut (14)
8. Turboréacteur comportant un moteur selon l'une des revendications 1 à 7 dont le premier module (A) comprend une soufflante (S) montée sur ledit arbre de puissance (3). 8. Turbojet engine comprising an engine according to one of claims 1 to 7, the first module (A) of which comprises a fan (S) mounted on said power shaft (3).
9. Turboréacteur selon la revendication 8 comprenant un deuxième module (B), en aval du premier module, le deuxième module comportant un rotor, formé d'un compresseur haute pression (1 b) et d'une turbine haute pression (1 d), et une chambre de combustion (1 d). 9. Turbojet according to claim 8 comprising a second module (B), downstream of the first module, the second module comprising a rotor, formed of a high pressure compressor (1 b) and a high pressure turbine (1 d) , and a combustion chamber (1 d).
10. Turboréacteur selon la revendication précédente comprenant un troisième module (C) avec une turbine basse pression (1 e), ledit arbre de turbine (2) étant solidaire du rotor de la turbine basse pression du troisième module. 10. Turbojet engine according to the preceding claim comprising a third module (C) with a low pressure turbine (1 e), said turbine shaft (2) being integral with the rotor of the low pressure turbine of the third module.
1 1 . Turboréacteur selon l'une des revendications 8 à 10, comprenant trois modules successifs, ledit premier module avec un rotor de soufflante et le compresseur basse pression, un deuxième module avec un rotor formé d'un compresseur haute pression et d'une turbine haute pression et une chambre de combustion et un troisième module avec un rotor de turbine basse pression et un arbre de turbine coaxial avec le rotor haute pression et relié au rotor de soufflante par l'intermédiaire du réducteur de vitesse, ce turboréacteur étant du type multiflux. 1 1 . Turbojet according to one of claims 8 to 10, comprising three successive modules, said first module with a fan rotor and the low pressure compressor, a second module with a rotor formed by a high pressure compressor and a high pressure turbine and a combustion chamber and a third module with a low pressure turbine rotor and a turbine shaft coaxial with the high pressure rotor and connected to the fan rotor via the speed reducer, this turbojet being of the multiflow type.
PCT/FR2014/052846 2013-11-21 2014-11-06 Modular engine, such as a jet engine, with a speed reduction gear WO2015075345A1 (en)

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EP14806028.8A EP3071792B1 (en) 2013-11-21 2014-11-06 Modular engine
RU2016119153A RU2674098C1 (en) 2013-11-21 2014-11-06 Modular engine, such as jet engine, with speed reduction gear
US15/037,397 US10473035B2 (en) 2013-11-21 2014-11-06 Modular engine, such as a jet engine, with a speed reduction gear
CA2929947A CA2929947C (en) 2013-11-21 2014-11-06 Modular engine, such as a jet engine, with a speed reduction gear
BR112016011122-2A BR112016011122B1 (en) 2013-11-21 2014-11-06 MODULAR STRUCTURE ENGINE AND TURBOREATOR THAT INCLUDES SUCH ENGINE
CN201480063462.6A CN105765166B (en) 2013-11-21 2014-11-06 The modular engine with gear reduction unit of such as jet engine

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FR1361460A FR3013388B1 (en) 2013-11-21 2013-11-21 ENGINE, SUCH AS A TURBOJET, MODULAR WITH SPEED REDUCER

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019122739A1 (en) 2017-12-22 2019-06-27 Safran Aircraft Engines Dynamic sealing between two rotors of an aircraft turbomachine
WO2019122625A1 (en) 2017-12-22 2019-06-27 Safran Aircraft Engines Dynamic seal bewteen two rotors of an aircraft turbine engine
DE102019102450A1 (en) * 2019-01-31 2020-08-06 Rolls-Royce Deutschland Ltd & Co Kg Method for assembling a transmission module of a gas turbine engine
DE102019102429A1 (en) * 2019-01-31 2020-08-06 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine engine for an aircraft
FR3115823A1 (en) 2020-11-04 2022-05-06 Safran Aircraft Engines MODULARITY OF AN AIRCRAFT TURBOMACHINE
FR3115822A1 (en) 2020-11-04 2022-05-06 Safran Aircraft Engines MODULARITY OF AN AIRCRAFT TURBOMACHINE

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3013385B1 (en) * 2013-11-21 2015-11-13 Snecma PRE-SEALED SPEAKER DURING MODULAR DISASSEMBLY OF A REDUCING TURBOREACTOR
FR3046202B1 (en) 2015-12-24 2017-12-29 Snecma TURBOREACTOR WITH MEANS OF PUSH RESUME ON THE INTER-COMPRESSOR HOUSING
FR3046201B1 (en) * 2015-12-24 2018-01-19 Safran Aircraft Engines TURBOREACTOR WITH MEANS OF PUSH RESUME ON THE INTER-COMPRESSOR HOUSING
BE1025131B1 (en) * 2017-04-11 2018-11-14 Safran Aero Boosters S.A. DOUBLE-CURVED TRANSMISSION SHAFT FOR TURBOMACHINE
US11168828B2 (en) 2017-05-02 2021-11-09 Pratt & Whitney Canada Corp. Gas turbine engine casing arrangement
FR3086343B1 (en) * 2018-09-24 2020-09-04 Safran Aircraft Engines TURBOMACHINE WITH REDUCER FOR AN AIRCRAFT
FR3087819B1 (en) * 2018-10-26 2020-11-13 Safran Aircraft Engines AIRCRAFT TURBOMACHINE EQUIPPED WITH AN ELECTRIC MACHINE
GB201817937D0 (en) * 2018-11-02 2018-12-19 Rolls Royce Plc Gas turbine engine
GB201903703D0 (en) * 2019-03-19 2019-05-01 Rolls Royce Plc A gas turbine engine bearing support structure
US11174916B2 (en) 2019-03-21 2021-11-16 Pratt & Whitney Canada Corp. Aircraft engine reduction gearbox
CN109854377B (en) * 2019-04-08 2024-05-03 沈阳建筑大学 Novel aviation turbofan engine
US11365630B1 (en) * 2020-12-28 2022-06-21 Rolls-Royce North American Technologies Inc. Fan rotor with tapered drive joint
US11268453B1 (en) 2021-03-17 2022-03-08 Pratt & Whitney Canada Corp. Lubrication system for aircraft engine reduction gearbox
CN112983651B (en) * 2021-04-26 2023-07-28 黄锴 Small aviation double-rotor unmanned aerial vehicle engine
FR3140123A1 (en) 2022-09-26 2024-03-29 Safran Aircraft Engines MODULARITY OF AN AIRCRAFT TURBOMACHINE BY AN AXIAL AND ROTATIONAL LOCKING DEVICE, CORRESPONDING ASSEMBLY METHOD
FR3140124A1 (en) * 2022-09-26 2024-03-29 Safran Aircraft Engines TURBOMACHINE COMPRISING SEVERAL MODULES AND A DEVICE FOR BLOCKING THESE MODULES, AND CORRESPONDING DISASSEMBLY METHOD

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1813792A1 (en) * 2006-01-30 2007-08-01 Snecma Engine shaft linking system with retractable nut
US20090081039A1 (en) * 2007-09-25 2009-03-26 Mccune Michael E Gas turbine engine front architecture modularity
EP2327859A2 (en) * 2009-11-30 2011-06-01 United Technologies Corporation Mounting system for a planetary gear train in a gas turbine engine
US20120257960A1 (en) * 2009-11-20 2012-10-11 United Technologies Corporation Engine Bearing Support
US8402741B1 (en) * 2012-01-31 2013-03-26 United Technologies Corporation Gas turbine engine shaft bearing configuration

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2866073B1 (en) * 2004-02-11 2006-07-28 Snecma Moteurs TURBOREACTOR HAVING TWO SOLIDARITY CONTRAROTATIVE BLOWERS OF A CONTRAROTATIVE LOW-PRESSURE COMPRESSOR
ITFI20110269A1 (en) * 2011-12-12 2013-06-13 Nuovo Pignone Spa "TURNING GEAR FOR GAS TURBINE ARRANGEMENTS"
EP3456940B8 (en) * 2011-12-30 2020-11-04 Raytheon Technologies Corporation Gas turbine engine lubrication

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1813792A1 (en) * 2006-01-30 2007-08-01 Snecma Engine shaft linking system with retractable nut
US20090081039A1 (en) * 2007-09-25 2009-03-26 Mccune Michael E Gas turbine engine front architecture modularity
US20120257960A1 (en) * 2009-11-20 2012-10-11 United Technologies Corporation Engine Bearing Support
EP2327859A2 (en) * 2009-11-30 2011-06-01 United Technologies Corporation Mounting system for a planetary gear train in a gas turbine engine
US8402741B1 (en) * 2012-01-31 2013-03-26 United Technologies Corporation Gas turbine engine shaft bearing configuration

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019122739A1 (en) 2017-12-22 2019-06-27 Safran Aircraft Engines Dynamic sealing between two rotors of an aircraft turbomachine
WO2019122625A1 (en) 2017-12-22 2019-06-27 Safran Aircraft Engines Dynamic seal bewteen two rotors of an aircraft turbine engine
US11220929B2 (en) 2017-12-22 2022-01-11 Safran Aircraft Engines Dynamic sealing between two rotors of an aircraft turbomachine
US11352906B2 (en) 2017-12-22 2022-06-07 Safran Aircraft Engines Dynamic sealing between two rotors of an aircraft turbomachine
DE102019102450A1 (en) * 2019-01-31 2020-08-06 Rolls-Royce Deutschland Ltd & Co Kg Method for assembling a transmission module of a gas turbine engine
DE102019102429A1 (en) * 2019-01-31 2020-08-06 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine engine for an aircraft
DE102019102450B4 (en) 2019-01-31 2023-07-20 Rolls-Royce Deutschland Ltd & Co Kg Method of assembling a gear module of a gas turbine engine
FR3115823A1 (en) 2020-11-04 2022-05-06 Safran Aircraft Engines MODULARITY OF AN AIRCRAFT TURBOMACHINE
FR3115822A1 (en) 2020-11-04 2022-05-06 Safran Aircraft Engines MODULARITY OF AN AIRCRAFT TURBOMACHINE
WO2022096814A1 (en) 2020-11-04 2022-05-12 Safran Aircraft Engines Modularity of an aircraft turbomachine
WO2022096813A1 (en) 2020-11-04 2022-05-12 Safran Aircraft Engines Modularity of an aircraft turbomachine
US11933230B2 (en) 2020-11-04 2024-03-19 Safran Aircraft Engines Modularity of an aircraft turbomachine

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RU2674098C1 (en) 2018-12-04
FR3013388A1 (en) 2015-05-22
EP3071792A1 (en) 2016-09-28
BR112016011122A2 (en) 2017-08-08
BR112016011122B1 (en) 2022-04-12
RU2016119153A (en) 2017-12-26
US10473035B2 (en) 2019-11-12
FR3013388B1 (en) 2019-03-22
CA2929947C (en) 2022-12-06
CN105765166B (en) 2019-04-05

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